EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH STALL MANAGEMENT ú
27-32-00
COMPUTER P/N 65-52822 ú CONFIG 2
ú 01 Page 3
ú Mar 15/90
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
4. Stall Management Computer (Fig. 1)
_________________________
A. Each stall management computer (SMC) uses information from the AOA sensor, the flap position transmitter, and other airplane systems to determine whether to activate the control column shaker. The SMC's are located on the E1-1 electronics shelf.
B. The airplane configuration changes the AOA angle at which the stall management system signals a stall condition. The airplane configuration is read by the stall management system from the program data bits which are on the Stall Management Computer. The program input bits can be displayed through the SMC BITE. A comparision of the program data bits takes place every second between SMC's. When the SMC's disagree, a configuration message will appear on either or both SMC's. The inputs are numbered for identification for use by the SMC system and are listed in the table below.
(1)
You can check the program word wiring using the SMC Bite. The BITE system configuration and the input discrete displays to compare the program data bits listed by the SMC against and the configuration for your airplane.
(2)
The table below lists the program data bits. Grounding a program pin enables the function listed in the table. Leaving a program pin open disables that function for the stall management calculations.
~...................................................................... | PROGRAM PIN ASSIGNMENT (Enable) | CONFIGURATION OPTION | ........................................................................ | 0 |Pitch Limit Indicator | ........................................................................ | 1 |-400 Thrust Bias | ........................................................................ | 2 |-300/-500 Flap Compensation | ........................................................................ | 3 |CAA Certification | ........................................................................ | 4 |Electronic Flight Information System| ........................................................................ | 5 |Stall Management Computer | 2.................................…....................................1
C. SMC 1 activates the captain's control column shaker. SMC 1 is powered by 28 volts dc through a circuit breaker on the P18-2 panel from the standby bus. SMC 1 receives inputs from the following sources:
(1)
Left AOA Sensor
(2)
Right Flap Position Transmitter
(3)
EIS Primary Display
(4)
Landing Gear Logic Shelf
(5)
Left Main Gear Downlock Switch
(6)
Leading Edge Flaps and Slats Position Indication Module
(7)
Left Air Data Computer
(8)
Left Inertial Reference Unit
(9)
Flight Management Computer
(10)
Takeoff/Go-Around Switches at Thrust Levers
(11)
STALL WARNING TEST NO. 1 Switch on P5-18 module
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH STALL MANAGEMENT ú
27-32-00
COMPUTER P/N 65-52822 ú CONFIG 2 ú 03 Page 4 ú Nov 15/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
D. SMC 2 activates the first officer's control column shaker. SMC 2 is powered by 28 volts dc through a circuit breaker on the P6-1 panel from the electronics power bus No. 2. SMC 2 receives inputs from the following sources:
(1)
Right AOA Sensor
(2)
Left Flap Position Transmitter
(3)
EIS Primary Display
(4)
Landing Gear Logic Shelf
(5)
Right Main Gear Downlock Switch
(6)
Leading Edge Flaps and Slats Position Indication Module
(7)
Right Air Data Computer
(8) 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：737-300 400 500 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 3(28)
